Mooney M20TN, Руководство по обслуживанию и ремонту

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MOONEY AVIATION COMPANY, INC.
M20TN SERVICE & MAINTENANCE MANUAL
Page
Date
13
2006
Rev Date
K. Start turnbuckle eye attached to forward cable
end into barrel. Tighten turnbuckle barrel until tension
JUST begins on spring.
L. Repeat steps I. through K. on the aft spring and
cable end.
M. Verify that required number of threads are
screwed into both turnbuckle barrels.
N. Remove spring extenders from both springs.
Remove tape from cable and capstan and rudder lock
from rudder.
NOTE:
After basic rigging is complete, install any re-
moved components. Reconnect aileron--rudder
interconnect system. Verify electrical alignment.
Remove rudder lock.
O. The rudder should be “neutral” at 3 to 5
o
left rud-
der.
P. Electrically run actuator for right rudder deflec-
tion. The actuator motor should stop when rudder is de-
flected 23
o
right. If not, slightly bend forward limit
switch’s (RIGHT rudder stop) actuator arm to position
right rudder at 23
o
. Cycle system and recheck right rud-
der deflection.
Q. The TRIM LIMITS are: 3 to 5
o
LEFT; 23
o
RIGHT.
R. Secure aft turnbuckle and make sure there is no
interference between rudder trim mechanism and flight
control tubes or bellcranks during cycle or full travel of
flight control surfaces.
2. Rudder Trim Indicator – Rigging
A. Use rudder trim switch in aircraft to run rudder
trim full right.
B. Adjust potentiometer on motor/cable assembly
per instructions provided in the GARMIN G1000 Main-
tenance Manual.
C. Remove rudder travel board. Re--install access
cover and belly skin.
D. Flight test aircraft. Rudder trim shall center turn
coordinator ball with no pilot application of rudder dur-
ing full power climbs at 105 KIAS. If it does not, gain ac-
cess to forward turnbuckle and tighten an additional .25
to .38 inch extension of forward spring. Secure forward
turnbuckle.
E. Complete log book entry and return aircraft to
service or complete remaining maintenance action.
27--41--00 -- Stabilizer Trim System Troubleshoot-
ing
BINDING Check control tubes at bulk-
head grommets for rub
marks.
Check Trim Actuator threads
for galling or not lubricated.
Lubricate per Sect. 5.
ELECTRIC
CLUTCH SLIP-
PING
Check BINDING symptoms
above.
Check for proper clutch set-
tings per vendor instruc-
tions.
Confirm full bus voltage is
available at trim motor.
NOTE:
Maximum wear on trim tube, where it passes
through bulkhead grommets, is .007 inch per wall
or .014 inch diameter.
27--42--00 -- ELECTRIC PITCH TRIM SYSTEM (OP-
TIONAL)
If installed, optional auto--pilot Electric Pitch Trim Sys-
tem components require periodic maintenance. Sys-
tem components must be inspected and lubricated per
the vendor service and maintenance procedures:
To gain access to the servo area, remove electrical bay
access cover from left hand side of tailcone. Locate
Electric Pitch Trim servo system, just aft of Fuselage
Sta. 142 bulkhead. Inspect system per vendor recom-
mendations.
If Pitch Trim System bearing block assembly replace-
ment is required, refer to following procedures:
Trim torque tube/pitch trim servo assembly should be
removed from aircraft to replace bearing block, there-
fore, manual trim wheel and electric trim switch should
be flagged so inadvertent movement will not occur.
1. Disconnect universal joint located between tail-
cone bulkhead, Sta. 142, and pitch trim servo assembly
mounting brackets.
2. Disconnect electrical wiring, to servo motor, at
connector.
3. Disconnect ELT harness from connector and any
other wiring that may interfere with the removal of
torque tube assembly from tailcone.
4. Remove nuts, washers, bolts/screws from upper
and lower pitch trim servo brackets holding brackets to
bulkhead.
5. Carefully lift torque tube/pitch trim servo assembly
up and pull aft end of torque tube from trim actuator
socket on aft tailcone bulkhead. Support aft end of
torque tube if needed.
6. Pull torque tube/trim servo assembly from tailcone
through access cover on left side of tailcone.
27--42--00